Apparatus and methods for linear actuation of flow altering components of jet engine nozzle

Abstract

A trans cowl for a jet engine includes a chevron coupled with a linear actuators. The chevron is movable by the linear actuator forward or aft to change a gas flow path formed by an core cowl and thrust reverser translating cowl. In a first position, the chevrons are disposed substantially parallel the gas flow path to attenuate drag and/or loss of engine thrust. In a second position, the chevrons are moved aft to project, or further project, into the gas flow path. In one embodiment, the linear actuator comprises a first component that is coupled with the outer cowl. A second component of the linear actuator is coupled with the chevron. When installed, the linear actuator can be coupled with a controller and an electrical power source. A position sensor coupled with the controller senses a position of the linear actuator and/or the chevron.

What is claimed is: 
     
       1. An apparatus for positioning a chevron, said apparatus comprising:
 a linear actuator; 
 a chevron having a base end configured to fit within a corresponding channel on a translating cowl; 
 a pair of guide members secured to the translating cowl and slidably engaged with opposite edges of the chevron, 
 wherein the chevron is movable by the linear actuator forward or aft to change the position of the chevron relative to the gas flow path, and 
 wherein the chevron comprises a slot that is sized and configured to receive a rotor of the linear actuator therein. 
 
     
     
       2. The apparatus of  claim 1 , wherein the guide members comprise a linear slide. 
     
     
       3. The apparatus of  claim 1 , further comprising:
 a housing, assembly that can be secured to each of the outer cowl and the chevron, wherein the housing assembly encloses the linear actuator therein. 
 
     
     
       4. The apparatus of  claim 1 , further comprising:
 a position sensor coupled to a controller on an aircraft, the position sensor configured to output data to the controller indicative of a position of the linear actuator and/or a position of the chevron. 
 
     
     
       5. An apparatus for changing a gas flow path formed in a jet engine by an inner cowl and an outer cowl, comprising:
 a chevron having a base end configured to fit within a corresponding channel on a translating cowl; 
 a linear actuator coupled to the chevron and to the translating cowl of the jet engine, 
 wherein the chevron is translatable by the linear actuator forward or aft to change the position of the chevron relative to the gas flow path, and 
 wherein the chevron comprises a slot that is sized and configured to receive a rotor of the linear actuator therein. 
 
     
     
       6. An apparatus for changing a gas flow path formed in a jet engine by an inner cowl and an outer cowl, said apparatus comprising:
 a chevron; 
 a linear actuator coupled to the chevron and to an outer cowl of the jet engine; 
 a tang disposed on the chevron, wherein the tang forms a clevis fitting with opposing structural members of the linear actuator; and 
 a housing assembly, 
 wherein the housing assembly comprises a first housing coupled to an outer surface of an outer member of said outer cowl, and 
 wherein the housing assembly comprises a second housing that is coupled to an outer surface of the chevron, and wherein the second housing slidably fits with the first housing, and 
 wherein the chevron is movable by the linear actuator forward or aft to change the position of the chevron relative to the gas flow path. 
 
     
     
       7. The apparatus of  claim 6 , further comprising a controller coupled with the linear actuator. 
     
     
       8. The apparatus of  claim 7 , further comprising a position sensor coupled with the controller and configured to output data to the controller indicative of a position of the linear actuator and/or a position of the chevron. 
     
     
       9. The apparatus of  claim 6 , wherein in a first position, the chevron is disposed substantially parallel to the gas flow path to attenuate drag and/or loss of engine thrust. 
     
     
       10. The apparatus of  claim 9 , wherein in a second position, the chevron is translated aft to project into the gas flow path. 
     
     
       11. An apparatus for positioning a chevron, said apparatus comprising:
 a linear actuator; 
 a chevron having a base end configured to fit within a corresponding channel on a translating cowl; 
 a guide member secured to the translating cowl and the chevron; 
 a support structure that forms a clevis fitting with the chevron; and 
 a housing assembly, 
 wherein the housing assembly comprises a first housing coupled to an outer surface of an outer member of said translating cowl, and 
 wherein the housing assembly comprises a second housing that is coupled to an outer surface of the chevron, and wherein the second housing slidably fits with the first housing, and 
 wherein the chevron is movable by the linear actuator forward or aft to change the position of the chevron relative to the gas flow path. 
 
     
     
       12. The apparatus of  claim 11 , wherein the support structure comprises opposing structural members and a pin that interfaces with a tang disposed on the chevron. 
     
     
       13. A translating cowl comprising:
 a chevron; 
 a linear actuator coupled with the chevron; and 
 a housing assembly coupled to the chevron, 
 wherein the housing assembly is configured to house the linear actuator and to permit translation of the linear actuator to extend and retract the chevron relative to the gas flow path, 
 wherein the chevron is movable by the linear actuator forward or aft to change the position of the chevron relative to the gas flow path, 
 wherein the housing assembly comprises a first housing coupled to an outer surface of an outer member of said translating cowl, and 
 wherein the housing assembly comprises a second housing that is coupled to an outer surface of the chevron, and wherein the second housing slidably fits within the first housing. 
 
     
     
       14. The translating cowl of  claim 13 , further comprising a controller coupled With the linear actuator. 
     
     
       15. The translating cowl of  claim 14 , further comprising;
 a position sensor coupled with the controller and configured to output data to the controller indicative of a position of the linear actuator and/or a position of the chevron. 
 
     
     
       16. The translating cowl of  claim 13 , wherein in a first position, the chevron is disposed substantially parallel to the gas flow path to attenuate drag and/or loss of engine thrust. 
     
     
       17. The translating cowl of  claim 16 , wherein in a second position, the chevron is translated aft to project into the gas flow path. 
     
     
       18. The translating cowl of  claim 13 , wherein the linear actuator is coupled with an outer member of the translating cowl. 
     
     
       19. The translating cowl of  claim 18 , wherein the chevron has a base end that is disposed in a channel formed between the outer member and an inner member of the translating cowl.